Kazan Helicopters Mi-17-1V Flight Manual page 153

MI1-17-1B. Flight manual
as follows:
1) Reduce the main rotor collective pitch down to the minimum
level and further on, in the course of descent operate the col-
lective pitch control lever to maintain the main rotor speed
within the limits of 98 to 100 %.
2) Shut down the engine by closing the HP fuel shutoff valves,
give an order to the Flight Engineer to close the fuel fire shut-
off valves and switch off the fuel booster and transfer pumps.
3)
Accelerate or decelerate the helicopter to establish a gliding
speed of 100 to 120 kmlh lAS.
4) Select a landing area so as to land into the wind.
5) At a height of 60 to 70 m begin vigorously reducing the for-
ward speed to 60 to 70 kmlh by pitching up the helicopter.
6) At a speed of 60 to 70 kmlh begin smooth reduction of pitch
angle so as it would be close to the landing value (4 to 6°) by
the moment of touchdown.
7) At a height of 10 to 20 m begin reducing the vertical speed by
rapid and continuous increase of the main rotor collective
pitch at a rate of 6 to 8 deg/s.
8) While increasing the main rotor collective pitch maintain the
landing pitch attitude by small deflection of the control stick
forward.
9) After touchdown push the collective pitch control lever fully
down with simultaneous application of the control stick
1/3
to
1/4 full travel forward and apply the LG wheel brakes.
(b) If the area selected for landing is outside of course or a necessity to
change the landing course arises due to the wind direction (pro-
vided the altitude margin is adequate) execute a required manoeu-
vre in steady autorotation condition.
The altitude should be not less than 650 m to execute autorotation
landing with a 180-degree turn and bank of 15°.
(c) In case of failure of both engines at altitude below 100 m and air-
speed above 120 kmlh proceed as follows:
1) Immediately push the collective pitch control lever fully down
with simultaneous proceeding to vigorous slowing down of the
forward speed by pitching up the helicopter to 15 to 20°.
2) Shut down the engine by closing the HP fuel shutoff valves,
give an order to the Flight Engineer to close the fuel fire shut-
off valves and switch off the fuel booster and transfer pumps.
3)
Upon attainment of a speed of 50 to 60 kmlh initiate smooth
reduction of the pitch angle so as the helicopter pitch attitude
would be close to landing one (4 to 6°) by the moment of
touchdown.
4) At a height of 10 to 20 m begin reducing the vertical speed by
rapid and continuous increase of the main rotor collective
pitch at a rate of 6 to 8 deg/s.
5) While increasing the main rotor collective pitch maintain the
landing pitch attitude through small deflection of the control
stick forward.
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